The camber and gradient can be scaled linearly to the required Cl value. Of the maximum camber at a coefficient of lift (Cl) value of 0.3. Details of airfoil (aerofoil)(naca23012-il) NACA 23012 12 NACA 23012 airfoil Plot Airfoil Reynolds Ncrit Max Cl/Cd Description Source naca23012-il 50,000 9 24.2 at 4. The values for the constants r, k 1 and k 2/k 1 are tabulated for various positions There are also different equations for standard and reflex camber lines. The equation for the camber line is split into two sections like the 4 digit series but the division between the two sections is not at the point of maximum camber. The tests were made in the NACA 7 by 10-foot and variable-density wind tunnels and covered a range of Reynolds numbers that included values corresponding to those for landing conditions of a wide range. The maximum thickness as percentage.In the examble XX=12 so the maximum thickness is 0.12 or 12% chord. NACA 4 Series Airfoil Generator Wing Plot Tool All Calculators About Calculators All of the AeroToolbox calculators in one convenient place Atmosphere and Airflow properties Standard Atmospheric calculator based on the US Standard Atmosphere of 1976. Report presents the results of an investigation of the general aerodynamic characteristics of the NACA 2301 airfoils, each equipped with a 0.20c external flap of NACA 23012 section. In the examble P=3 so maximum camber is at 0.15 or 15% chordĠ = normal camber line, 1 = reflex camber line What is odd to me though is that if I ring up a NACA 23012 on Compufoil it looks nothing like a light plane airfoil, but a 28012 is not too different from the Clark-Y or USA35B. The position of maximum camber divided by 20. It indicates the designed coefficient of lift (Cl) multiplied by 3/20. NACA 5 digit airfoils in the database NACA 22112 NACA 23012 NACA 23015 NACA 23018 NACA 23021 NACA 23024 NACA 23112 NACA 24112 NACA 25112 Design coefficient of lift
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